Lifting propeller



Feb. 24, 1931- J. M. BUNN LIFTING PROPELLER Filed April 17, 1930 2 Sheets-Sheet 1 Feb. 24, 193.1. 1,194,277

LIFTING PROPELLER Filed April 17, 1930 2 Sheets-Sheet 2 hmunulm m:

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Patented Feb. 24, 1931 UNITED STATES PATENT orr'rc Application filed April 17,

My invention relates to improvements in aeroplanes and has for its object to provide means for increasing the buoyance and stability of the aeroplane while in flight.

A further object of the invention is to rovide an aeroplane having air cham ers formed in the fuselage and wings and means for driving air into the air chambers whereby the buoyance of the aeroplane is increased.

Another object of the invention is to provide means of the above-mentioned character which is simple and durable in construction, reliable and efiicient in operation and inexpensive to manufacture.

Other objects and advantages of the invention will be apparent during the course of the following description.

In the accompanying drawings, formin a part of this specification and in which like numerals are employed to designate like parts throughout the same,

Fig. 1, is a side elevational view of an aeroplane embodying my improvements,

Fig. 2, is a front view of the same, partly in section,

Fig. 3, is a top plan view partly in section, and

Fig. 4, is across section taken on lines 4-4 of Fig. 1. In the drawings, wherein for the purpose of illustration, I have shown a preferred embodiment of my invention, the numeral 5 denotes the fuselage of an aeroplane, which in the present instance-has its side and top walls 6 formed with inner spaced walls 7, providing air passages 8 extending longitudinally of the fuselage for its entire length, the passages being open at the tail end of the The wings 9 of the aeroplane are of hollow construction throughout their length providing air passages 10 within the wings, which passages communicate with the longitudinal air passages 8 of the fuselage, at the ointure of the wings with the fuselage, as shown more clearly in F ig; 2.

The bottom of the fuselage directly above the landing gear 11 of the aeroplane'is open and within this open space is disposed a propeller 12 which is mounted on the lower end of the vertical shaft 13. The shaft 13 is consize and arrangement of the parts ma 1930. Serial No. 445,076.

nected with and driven by the motor of the aeroplane, not shown, or if desired may be driven by the air driven backby the main propeller 14 mounted at the forward end of the fuselage. The inner walls of the air passages 8 in the sides of the fuselage, directly opposite the propeller 12 are provided with air inlet openings 15, through which the air is forced by the propeller 12 into the air pas sages. The rear longitudinal edges of the wings 9 are provided at spaced intervals with a seriesvof air outlet openings 16, through which the air introduced into the wings is exhausted. e

In operation, it willbe seen that when the propeller 12 is rotated it creates a current of air which is forced through the openings 15 into the air passages tributed to the air passages 10 of the wings and discharged from the passages 8 at their open. ends and the passages 10 through the openings 16 of the wings. This current of air introduced into the passages 8 and 10 increases the buoyancy of the aeroplane, so that the aeroplane can rise moreeasily and ingreisting the stability of the plane while in 1g It is to be understood that the form of my invention, herewith shown and described is to be taken as a preferred example of the same and that certain changes in the shape, be made without departing from the spirit of the invention or the scope of the subjoined claims.

Having thus described claim 1. In an aeroplane having a rearwardly tapering I coextensive with the sides and top of the fuselage, air passages formed in the wings of by invention, 1

the aeroplane having communication with said longitudinal air passages, the respective passages having restricted exhaust openings at their rear ends and means for forcing air into said air passages through a common intake.

2. In an aeroplane having a rearwardly tapering fuselage, longitudinal air passa es formed in the fuselage and coextensive with 8, from where it is disfuselage, longitudinal air passages the sides and top thereof, said air passages having their rear ends open, air passages formed in the wings of the aeroplane having communication with said longitudinal air 5 passages, a recessed compartment in the bottom of the fusela e having a propeller operatively mounted t erein for drawing air into the compartment and air intakes'for the air passages at the sides of said compartment. In testimony whereof I aflix Ifiy si ature.

JAMES B 

